Starting system for gas turbine engines



Feb. 2, 1954 A. A. KUZMlTZ 2,667,742

STARTING SYSTEM FOR GAS TURBINE ENGINES Filed Feb. 24, 1947 6 Sheets-Sheet 1 lA/l/f/VTO/S 44 914 517. 97/7/72 Feb. 2, 1954 A. A. KUZMlTZ STARTING SYSTEM FOR GAS TURBINE ENGINES 6 Sheet'sQSheet 2 Filed Feb. 24. 1947 Z H mm m 0 m! MM. w I 0 7 N y W 6,13 \\\|J m hm N $W \h N. \N

Feb. 2, 1954 A. A. KUZMITZ STARTING SYSTEM FOR GAS TURBINE-ENGINES 6 Sheets-Sheet 3 Filed Feb. 24, 1947 JNVENTOR. )4/V0/Pf/V 14. [WI/W72 Feb. 2, 1954 A. A. KUZMITZ STARTING SYSTEM FOR GAS TURBINE ENGINES 6 Sheets-Sheet 4 Filed Feb. 24, 1947 Feb, 2, 1954 Filed Feb. 24, 1947 A. A. KUZMITZ STARTING SYSTEM FOR GAS TURBINE ENGINES 6 Sheets-Sheet 5 PRES I? /4/Z' DE ZRGE AESSZ /7f #40 k I M5 W36 COMP. lNLEL PR$S.& TIME w W /25 /26 /?4 5g5 i Q mi '7 W Feb. 2, 1954 A. A. KUZMITZ STARTING SYSTEM FOR GAS TURBINEL ENGINES 6 Sheets-Sheet 6 Filed Feb. 24, 1947 hu lmhfi Patented Feb. 2, 1954 smimrma sxs'mM FOR ens TURBINE) mamas AndrewA ,Kuzmitz. South R n assignouo Bendix Aviation Gorpp 'ation smith Bend, mputation of Delaware Anpfieationrebruarym, 1947, Serial No. 730,622 m: (i.',60-+3ii.1 4i

This inventionrelates to fuel supply andstarting systems .for gas .tunbine engines; it is par ticularly, but not necessarily, concerned with starting systems for gas turbine engines adapted for powering aircraft, as where the engine fum tions as a straight jet en'g'ine, agas turbine propeller engine, .or combines the functions" of .a jet engine and a propeller engine.

Among the objects oi 'tli'e invention are:

To o in Pressure at the fuel discha ge nozzles during starting sufficient to insure good spray atomization at relatively low cranking speeds;

To provide a iue'lvfeedl-and coordinated'i nition system wherein all or amajor portion ofith'ejuei sprayed into the burner system: during starting will be ignited so that a. minimum 0f raw fuel will enter the tail. cone hefo e combustion takes place in the entire burnersystemj; v I

To pr vide a startin systemjor engines of the above type which will pitoduce ignition at the burners and increase theengine speedpr R. ,P, M. to a, self-sustainin value in as short ta time as possible" without exceeding safe combustion tam perat'ures; r

A vstarting system ..cja7pa1i1eof Safe restarts in flight in theveyent nf'flaine blnwoutor dieout with a minimum .attention'ior manual effortby'an openaltorurpi'lnt; A

A startingisystem which wiiLprevent ,topmi'ch a fuel flow afterigniti niis iebtained' in the entire roup of burners, with consequent in temperature in the burner system Beynndea safe value;

A sta system wherein s arting: iiiei is initially conducted directly t0 the point of .ijgnition of one or more pilot burners-withqut enter,- ing and accumulating in ,a'iiianifold ling onother fuel receiving device ommon ltb all-burners;

An ignition system coordinated" with a- -fue1 sup y S m to obtain saie andlenicient starting underau conditions ofoperation; and

To generally im rove stertingisystems for gas turbine engines.

The fore ing and otherpobie ts end advantajges'will become; apparentin- View oi -the following description taken.'in -,c0n'iunctionwith the drawingswheiiein:

Figure 1- 'is a viewxin' eleveiticii andflpartly brokenaway of a gas tunbine---.engine fer aircraft equi ed with a starting systemain'eecordance with itheinventionz- Figure 2;. a schematic or diagrammetieviewof the startingsystem t Eigune-iz;

Figure 3"; a schematib view cafe-modified at rangement with respect 1 0 he M 5 3 011 ure 2; .v v Figure 4;, a schematic mew -.of another modification;- v 7 I Figures Sawfly-detail viewsin sectien of pants otf Ei ure .4 and t Figure 7,, a schematic View of a further modi fled-arrangement. ,The engine shown fer the purposes of ill-ustitationis-of the multiple burner type havingan eiectricaliignition system; but it- 'wiil be undenstoiod that while the inwentinn is primari y a aptedfor use with such type of e gin fit-is not necessarily limited thereto- This, he ieaeh ing of the invention may, incertain respects at least,- be qually applicable t gas tur in e gi'nes having a single or undivided annular burnerchamber, and thi' may a o e true Qfthe ignition system, which could; under certaines Bee s of he invention be Other thanelectrie; JQi' example], it could be by means ofthe six-called starting torch oirby a pilotfiamei Referring first to Figure V1', a gas tunbinePOWer plant in the farm; ofa turbojet enerally indicated at 1'0- eompicisie's siccrnpressor rotor asse nine rotdr assembly .iZYeiid-en exhaust unit 0. tail cpne i3, to" which is eonnected theeonven tiohial tail pipe and dischange nozzle in mac tibn' jet assembly; n t

rbine rotor assembly includes a nin v u ban 5; paced from" the uuter i .1 and mimeq with aserie's' o1 openings 1'6 for admitting com-.- pressed air into the tube; air adanter ,gr header'se'ctibn, generally indicated at 1-1,. i gig-1 tachabiy cqrinlectedto vthe trontend ofthe burner s bl fit comprises .a-plu'rality vof lair adapt rs I I one for eajuh comfius'ticn chamber, which r die t ai underi es'suretb said chambers-W re it enters the flame tubes -l;5-and-mixe with zthe fuel discharged from burner .no z'zles 18- to efiect combustion, t e expanded and .prodiiets sf v f mzzlid'iaiihir'aemiassm 1y L9 and then th-ro gh th'e blads of a tureineztto eite tjststi j the-flatter. I

The: compressor rotor assembly mounts a e Shown, 170 1013263831 linillef'pressure into t 'e" ai i e l' adapters-extenders I 7. h

The expanded air and products of combustion, after passing through the blades of the turbine 20, are discharged to the atmosphere through the tail zone and discharge nozzle to effect propulsion of an aircraft in which the enine may be mounted. A diffuser 22 is usually mounted in the tail cone I3. Propulsion may also be effected, in whole or in part, by a propeller, not shown, which would be driven from the turbine 20.

The various accessories which go to make up the complete power plant Ill are mounted at the front of the engine on a suitable streamlined casing 23. Among these accessories is the coordinated fuel feeding and ignition system of the present invention, one form of which is diagrammatically shown in Figure 2.

The fuel system includes the discharge nozzles I 8, Figure 1, also 24 and 25, Figure 2, to which fuel is supplied by way of a manifold ring 26 and a series of individual fuel lines 21 and 28, 28. The nozzles 24 and 25 have been given separate reference numerals since they also function as pilot or starter nozzles in a manner to be described. The manifold ring receives fuel from a main fuel conduit 29, having mounted therein a fuel control unit, generally indicated at 39, and which may be and preferably is substantially similar to that disclosed in the copending application'of Frank 0. Mock, Serial No. 716,154, filed January 13, 1946. In Figure 2, only the control lever and coacting parts of the unit 36 are shown, since the particular type of control unit is a matter of choice and forms no essential part of the present invention. The parts shown include a control lever 3|, having pivotally connected thereto the one end of a hollow link 32, the opposite extremity of said link being pivotally connected to a lever 33 secured on a shaft 34, which when rotated in a counterclockwise direction, compresses a governor spring, not shown, and thereby determines the setting of a fuel feed or governor valve, also not shown, which in turn determines the rate of fuel feed. A maximum speed adjusting eccentric is indicated at 35 and is adapted to be contacted by an extension 35 of the lever 33 when the lever 3| is rotated counterclockwise to high power output position. When the lever 3| is rotated in a clockwise direction to a predetermined setting, it engages an idle detent 38 and acts through an engine driven governor, not shown, to position a governor feed valve, also not shown, and maintain the fuel feed at a predetermined idling rate; and if it is rotated further in a clockwise direction, it engages a socalled locked poppet detent 39, at which point the governor feed valve is under direct manual control free of the governor. Further rotation in a clockwise direction brings the said lever 3| to a fully closed fuel cut-off position.

A fuel tank is indicated at 4B, and leading from this tank is a fuel conduit 4|, having a boost pump 43 therein, which may be of the electric type controllable from a remote point such as the pilot's compartment. The conduit 4! communicates with a conduit 42 having an engine driven pump 44 mounted therein; it has an inbuilt by-pass, not shown, with a by-pass valve set to maintain the delivery pressure within a predetermined value. The pump 44 delivers into either or both branch conduits 42' and/or 42" through a check valve 98. A starting fuel conduit 45 has its intake end communicating with the conduit 42"; it has two discharge points, one at 46 into the fuel conduit 29 downstream of the control unit 36 and the other at 4? into a manifold by-pass conduit 48, from which fuel may flow to the pilot nozzles 24 and 25 by way of T- connections 49 and 59 and pipes 5|, 5|. It will be noted that the fuel supplied to the nozzles 24 and 25 through the conduit 48 icy-passes the fuel manifold ring 26, although fuel may also be supplied to said latter nozzles direct from the manifold ring 26 by way of fuel lines 25 and 28' and pipes or fuel line sections 5|, 5i. The fuel lines 28, 28 discharge into 5|, 5! through check valves 52 and 53, to prevent back or return flow of fuel into the manifold ring when the starting system is functioning.

On the downstream side of the point 41 where the conduit 48 is tapped into the conduit 45 is a valve port 54, controlled in a manner to be described, and on the upstream side of the tap-in point 4'! is another valve port 55, also controlled in a manner to be described.

A pair of spark plugs are diagrammatically indicated at 58 and 59 and their coacting spark coils at 63 and El, the latter usually comprising a primary and secondary together'with a make-andbreak device functioning to provide a high voltage to the spark plugs from the low voltage battery source. Only one spark plug and coacting starting nozzle need be employed if desired, since once one of the burners is ignited, the flame will spread through so-called outer and inner crossover tubes indicated at 55 and 57 in Figure 1 to the remaining burners, and it will also spread by way of the nozzle diaphragm 19. However, by having two spark plugs and pilot burners equally spaced, or about 180 apart, the time required for the flame to spread to all the burners is naturally reduced.

The spark plugs 58 and 59 are electrically connected in series by a wire 62, which in turn is connected to a wire 63, leading to the one terminal 64 of a pressure switch 65, carried by a piston 65, mounted in a cylinder 6'! and normally urged toward closed position by a spring 88, the said cylinder being in fluid pressure communication in a, switch opening direction with fuel conduit 29. The opposite terminal 59 of switch 65 is connected by a wire 10 with the one terminal ll of a main control switch 72, the opposite terminal 13 of said latter switch being connected by a wire 14 with the positive terminal of a battery F5 or other suitable source of supply. The switch 12 is normally urged toward open position by a, spring 16, and as herein shown, it is adapted to be closed by a cam Tl, rotatable through movement of the lever 3| of the main fuel control unit 30, the contour of the cam being such that it closes switch 12 when the lever Si is in idle position but allows the spring 75 to hold the switch open at all other positions of the lever. Another convenient way of controlling switch 72 is through the idle detent 38, which may be arranged so that it closes the switch 712 when it is depressed by lever 3|.

The switch 65 also constitutes part of a thermal control circuit comprising a pair of normally closed thermal switches 18 and 19, each having a thermal element l8, 79 located at a point where it will respond quickly to changes in temperature in the region of discharge of the starting burners or combustion chambers fired by fuel from the pilot nozzles 24 and 25, said starting burners being indicated in Figure 2 at and 8|. These thermal switches 18 and 19 may be of any suitable type wherein whenthe thermal elements 18', I9 attain a predetermined temperature, for

- pilots compartment.

below a self-sustaining value, usually about 2000 R. P. M.; if so, the starter must be engaged. Since the switch 65 is at this time closed, the conduit 45 will be opened for passage of fuel around the fuel control unit, and ignition will take place at nozzles 24 and 25 in the manner heretofore described. When the temperature in the tail pipe attains a value such as will cause the thermal switches 78 and I9 to open, the valve 86 opens, whereupon the feed of fuel is through both conduits 29 and 45, until the pressure in 29 attains a preselected value and switch 65 opens and valve 90 closes, after which fuel feed is through the control unit 30 by way of the conduit 29 to the manifold ring 26 and thence to all the burner nozzles. Opening of switch 65 also cuts off the ignition circuit. The control lever 3| can then be advanced to accelerate as desired.

Figure 3 The system illustrated in Figure 3 is the same as that of Figure 2 except that an auxiliary fuel supply pump and coacting circuit has been added for supplying fuel to the engine in the event the main fuel supply system including the control unit 30 should fail. Parts in Figure 3 which correspond to analogous parts in Figure 2 have been given similar reference numerals. The auxiliary system comprises an auxiliary fuel pump I00, which receives fuel from a conduit IOI, communicating at its intake with the conduit 42 upstream of pump 44. The pump I is provided with a by-pass I02, having a by-pass valve I03 mounted therein. This auxiliary pump delivers into a conduit I04 provided with an auxiliary fuel control unit which may take the form of a valve I under manual control of the pilot from the A check valve I00 prevents backfiow of fuel in the conduit I04. The auxiliary control valve I05 may be by-passed by a conduit I01, which corresponds to the conduit 45 of Figure 2. In the conduit I01 is mounted the solenoid valves 86 and 90 heretofore described in connection with Figure 2, and between which is the inlet to the conduit 46 for conducting starting fuel direct to the starting nozzles 24 and 25.

Operation (Figure 3) For a normal start, the pilot turns on the boost r pump 43 and the auxiliary pump I00, valve 105 remaining closed. He then engages the starter (not shown) and cranks the engine to approximately 1000 R. P. M., moving the main fuel control lever 3| from cut-01f to idle position. Since switch 65 is then closed, the ignition circuit will be energized, the solenoid valve 86 closed, valve 90 opened and drip valve 92 closed. Fuel under pressure will then be free to pass to the starting nozzles 24 and 25 without entering the manifold ring 26. When burning is established in the pilot burners B0 and BI and the temperature attains a. predetermined value, say for example 500 F., the thermal switches 18 and 19 open, de-energizing the solenoid 85 so that valve 86 opens, whereupon pressure builds up in the conduit 29, the pressure switch 65 opens, the ignition circuit is 'deenergized and valve 00 closes. Fuel to all the burner nozzles will then be supplied through the main control unit 30 and the fuel pressure in the pilot burners will drop to a safe value, all the burners will ignite and the engine attain idling speed. It will thus be seen that the auxiliary pump I00 supplies the necessary fuel to start the pilot burners and quickly raise the manifold pressure to, for example, between 45 and 50 p. s. i. after which the engine driven pump 00 automatically supplies the fuel necessary to increase the engine speed to maximum idling, say 4000 R. P. M. If desired, or should a failure of the main fuel control render same necessary, the fuel necessary to maintain the engine in operation may be supplied through the auxiliary pump I 00 and auxiliary control unit I05. Under these circumstances, the lever 3I of the main fuel control 30 is used to close the switch I2, or else a separate control for the said switch should be provided.

To restart in flight, either the main fuel control unit or the auxiliary control may be used. In either case, substantially the same procedure may be followed as outlined in connection with Figure 2, except that the emergency pump I00 is used.

In both the main and modified systems of Figures 2 and 3, the same advantages are present. Thus, if for some reason ignition does not take place promptly in the pilot burners, the rate of fuel flow to the fuel manifold ring is limited to a point where it will not flood the engine and create a safety hazard; only two burners are used to start and the fuel pressure build-up for the starting nozzles is rapid, reducing the starting time as well as the amount of excess fuel metered to the engine prior to ignition; after burning in the pilot burners is assured, the manifold pressure is quickly raised to a value where flame propagation takes place; there is little manual attention required to start the engine and bring it up to a self-sustaining idle speed, and the danger of exceeding safe combustion temperatures is minimized; the fuel pressure at the starting nozzles is quickly brought to a value such as to produce a relatively wide cone or spray angle, thereby insuring prompt ignition, a feature of particular importance when making the restarts in flight when the engine may be windmilling and air flow through the burners high.

Figures 4, 5 and 6 The starting system of Figures 4, 5 and 6 includes among its advantages: metering of fuel to the burner system in relation to changes in altitude or air density and/or as a function of compressor pressure and hence turbine speed, and as a consequence, elimination, if desired, of thermal switches.

Referring to Figure 4, parts which correspond to similar parts in Figures 2 and 3 are given similar reference numerals and need not again be described.

A metering valve of the dashpot type is generally indicated at H0; it includes a cylinder I I0 having a piston I I I lidably mounted therein and carrying a metering pin or valve I I2, adapted to control the area of a metering orifice IE3. A spring IM normally urges the pin or valve II2 to its retracted position, inward movement (valve closing movement) resulting from admission of fuel under pressure into chamber H5 in a manner to be described. The fuel to be metered enters a chamber H0, then flows through orifice H3 and into outlet chamber 7.

A main starting by-pass conduit IE8 has its inlet end connected to the fuel conduit 42"; it conducts fuel to the chamber H0 and also to a branch conduit H9. From chamber N6 the fuel is metered into the chamber II! and thence through conduit I20 to the main fuel conduit 29 and the manifold 26. Preferably, but not 9-. necessarily a pressure reducing valvagshown. diagrammatically at: I 21I is provided to.- maintain. apredetermined. prwsure; in the starting; fuel flowing to-the starting system.

The conduitsiifi and IN! also conduct fuel. to the starting. nozzles 24 and 215: through a. quantity and limiting. valve whichis: known inthe art as ahydraul-ic fuse valve; gen.- erally indicated: at til, the: said value being designed to admit acertain predetermined. quantity of fuel to: the starting nozzles, and thereafter automatically close fl= flowoff'ueli tosaid nozzles. An example oi such a. value; is illustrated in- Figure: 6:; in the simplified form. shown: itv comprises a. cylindrical shell M, spanned by a wall I 23, formed. with cater new orifices or ports 23. and a central bleedor erifice I23"; Fuel or fluid. under pressure flows into a elmmber I 2dand' the: main bulk thereofflows through the calibrated ports or orifices 8.2-3! into a central. chamber 25 and thence out throng-1'1z restricted space or port I26 and. chamber I251. A certain. portion or the fuel. also: flows through: the restricted orifice. or bleedi 223 and acts on. a piston valve IZl, mounted tos1ide-i-l acylinder lizg against the resistance of alight returnsprin'g. 29 and. adapted to seat:- at. I21." and close port iiifi'when: itreaches its seated position. Theclosingi travel of the piston; is. determined by the drop thereacross, which: in: turnis a function cat: or is in proportion. to the flow. After. apredetermined: or measured. quantity oi has passed through the ports I23 and restriction; i261 the valve: I21 seats and fuel flow is cut off downstream of. the valve.

Fuel passed. by theafuse: valve I22 flow-s by way of conduits I; I3I and. parallel passages M5,. I36 and. I60 located in a housing: IiEr, see Figure- 5,170. a conduit I31 and. thento: the chamber N5: of the metering Valve H0". Referring to.- Eigure. 5-,. check valve I43 in passage I45 prevents backflowof fuel through said passage when piston Iil of metering valve III]: moves. back or to the. right through force of spring. M4,. the rate of move-= ment of said piston being varied as a fiunction.

of pressure and temperatu-rev of the air flowing tothe compressor and also as a function. of com pressor discharge pressure a bellows. or aneroid assembly I32 and/or a pressure respone s-ive bellows or aneroid assembly 533; note. Figure 5 in connection with. Figure 4- The aneroid assembly I32 comprises a spring. loaded. pressure and temperature-responsive bellows I32 which carries a valve adapted to vary the area of an orifice or port I35. formed. in the. passage I36, and said bellows may be and preferably is located at a point where it will. be subject toram pressure and temperature The aneroid assembly 533- may comprise an evacuated pressure-responsive spring. loaded bellows I31, whichv carries a valve I38, adapted to vary the area oran orifice or port I39 formed. in passage I40, the said. bellows- Etll being. mounted in and anchored atone end. toa housing, t il, to which compressor discharge pressure may be transmitted by way of a tube or conduit l E21.

Between the outer parallel passages 3E and tilt is the one-way flow passage provided with the check valve Hi3 which controls a port l id, the said check valve permitting flow throughsaid passage its only in a direction toward the one ber N5 of the metering valve Mil. It wili be obvious that when the piston IH clcsesor moves back to the right, fuel may escape from "piston chamber H 5 only by way of. either or boththe. outer passages; I36 andlor M9,; the rate of-escape I to be contacted: bypressureswitch w-hena the.

pressure in the fuel line 29 reaches argiyenyaluee for example, so. 13:. s. i.. Another. solenoid valive tea controls a. port. I51I- inthe: conduit Mi ug stream of theme-lye ill).- and branch-conduit: 29;. said valve I513 being provided with. a. coil. t5 2,, Gfiflr nected by wire 1153a witlr the mairr line wire A. A. switch preterably manually operable.- from: the pilots compartment; controls; energiaatiom the: electrical" starting circuit which; may be; sup plied by current trout a suitable-source: or potion? tiaLsuchaasabat-tery '15s. Anothenwire i51- eons meets the: line wire: I54 with the R31 oi the ignition circuit.

Operation (Figures 4, 5 and The pilot first turns on the boost. mung: 43 with the control lever M; in cut-oft positionpthen depresses the starter button. (not shown) and. when the engine attains a speed of approximately 1000 R. P. M., he turns on the ignition system by closing the 55,.mh1lch ina instance is: shown independent of. fuel; contmt unit:

The. drip valve 92' then; closes and the; coil. I52 of: the" normally closedrsolenorbdl valve I 50; becomes energized and opens. allowing: fine flow to the: manifold 26: through the pr reducing valve lZls and the: metering: valve H01;

When. the pressure in. the: manifold 281' hence in the: conduit at value or say 30' p. s i-., the switch. 65 closes. energizing the) coil. I l-8 of the: normally closed. solenoid valve; ifli, whereupon. this: valvev opens and tool under pressure flows: into. the chamber sac of til-refuse valve I22 and; a predetermined: or measimezli quantity of fuel: passes to the starting: nozzles: and also to chamber I Ii-Ei ofthe dashpot; mom check valve: I 43 (see Figure 519 fleecing: piston I if I to the lei't, feeding of'iiue'l to these being continued until the. valve. t2! seats; and closes the port ms (Figure 69 Ignitiouait the starting nozzles: ensues upon discharge of tuelz therefrom and the: pressure.- the starting: ers immediately rises. The ruck pressure mm. municated. to the chamber Hi5 of timezmetefincg valve I I0 causes: the. valve.- II.2 to; move to. left and restrict orifice I13 such that sufficient fuel will pass to the fuel manifold 26 by way of conduits I 25! and E9 to maintain a pressure therein will hold switch 65 olosed and produce sufiicient discharge of fuel from the burner nozzles I8 as will-permit ignition flame propagation when flame is communicated thereto fromthe starting burners. The 'quan tity offuelpassed to the starting burners by of the fuse valve H2 should be such asto' insureignition and burning in the-starting beforethe fuse valve closes. the valve m: of Figure 6 'cl0ses, 'the pressure at the starting: nozzles drops to the approximate pressure exist ing in the manifold 216; and when happens, the pressure in line.- litl drops..theszpzzos sure is relievedxinthe chamber His or.theslrretermg; valve 1'), permitting thepiston it tumors to the right, whereupon valve? lit met to the; manifold .25 through: the; orifice or port; He, the rate at which-this fuel is metered. Ia-ry aeezne ing as a function of entering air temperature and pressure and also as a function of compressor pressure or turbine speed. Fuel pressure now builds up in the manifold 26 and the turbine is brought up to idle speed at a safe combustion temperature. When the engine attains a suitable idle speed, the pilot moves the control lever 3I of the unit 30 to idle position and opens the switch I55, whereupon the engine or turbine may be controlled through the main fuel control unit 30.

It will be seen that the rate of fuel feed to the burner system during the starting period may be controlled so that it will be greater at ground level than at altitude, this being desirable due to the fact that less fuel is required at altitude in view of the reduced density or supply of air; and it will also be obvious that the rate of feed of the starting fuel may be varied in relation to compressor output, and since this varies in relation to turbine speed, the feed of starting fuel also becomes a function of engine speed.

To restart in flight, it is only necessary to close off fuel flow to the manifold by way of the control device 30, and when the manifold pressure drops to, for example, 15 p. s. i. or less, turn on the ignition switch I55.

Figure 7 The arrangement shown in Figure '7 is essentially a slight modification of Figure 4, and parts which have been previously described and shown in connection with Figure 4 and preceding fig ures have been given similar reference numerals.

Instead of the single pressure switch of Figure 4, a pair of manifold pressure switches I60 and I6I are provided and these switches carry switch elements or movable contacts I60 and I6I' arranged in series. The switch I60 is adapted to close against spring resistance at, for example, a manifold pressure of 15 p. s. i., while the switch I6I may be adapted to open at a manifold pressure of approximately forty pounds. When switch I60 closes with I6I closed and contact I60 engages terminal or contact I62, current flows from line wire I51 through wire I63, switch elements I6I, I60 and wire I64 to the coil I48 of solenoid valve I46. An orifice or bleed I65 is inserted in line 48 to limit the maximum pressure on the starting nozzles. The remaining structure of Figure '7 is sufficiently disclosed in Figure 4 to enable those skilled in the art to readily understand the same in view of the following description of operation.

Operation (Figure 7) The pilot turns on the boost pump and, if desired, the emergency or auxiliary pump 95, with the lever 3| of the control unit 30 in cut-off position. The starting motor (not shown) is then engaged and the engine cranked. At about 1000 R. P. M. the ignition switch I55 is closed, placing the starting system in operation. Sparking at the plugs 58 and 59 then ensues, the drip valve 92 closes and solenoid valve I50 opens and allows fuel to flow across metering valve IIO to fuel line 29 and hence to the manifold 26, the reducing valve I2I limiting the pressure in the starting line upstream of the metering valve IIO to a predetermined value. When the manifold pressure reaches say 15 p. s. i., pressure switch I60 closes and solenoid valve I46 opens, allowing fuel to flow to the starting nozzles 24 and 25 through orifice or bleed I65 and fuel line 48. The quantity of fuel passed by the orifice I65 may bring the pressure at the starting nozzles up to say p. s. i. while ignition is taking place and combustion increases in the starting burners; and in the meantime, fuel has passed through fuel lines I3I, I3I' to chamber II5 of metering valve II 0 and has moved needle IIZ to the left to restrict orifice II3 such that sufficient fuel will pass to the fuel manifold 26 to maintain a pressure therein which will hold pressure switch I60 closed and produce sufficient discharge of fuel from the burner nozzles I8 as will permit ignition and flame propagation when flame is communicated thereto from the starting burners. When the pressure in the manifold reaches say 40 p. s. i., the pressure switch I6I opens, thereby breaking the circuit to the solenoid valve I48, causing the pressure in fuel lines 48 and I3I to drop, whereupon needle 2 starts to retract, metering fuel to the manifold 26 as a function of engine speed and/or entering air density (see Figure 5). When the engine has attained the desired idle speed, or after it has attained a speed such that it can be controlled by the main control unit 30, switch I55 is opened, thereby closing solenoid valve I50 and shutting off the starting system. If desired, the switch I55 may be interconnected with the control unit 30 for automatic operation as in Figures 2 and 3.

To restart in flight, the lever 3| of the control unit 30 may be turned to cut-off position, and when the manifold pressure drops to 15 p. s. i., the ignition is turned on. The operation is then substantially the same as above described.

It will be understood that no attempt has been made herein to enumerate all of the advantages of the improved starting system or to state the various alternative methods of operation. The drawings and descriptive matter should therefore not be considered as limiting the invention, the scope of the latter being defined by the appended claims.

I claim:

1. In a fuel supply and starting system for gas turbine engines, a plurality of fuel nozzles arranged to discharge fuel under pressure for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, ignition means for said starting nozzle, a fuel manifold common to all of said nozzles including the starting nozzle, a main fuel conduit for conducting fuel to said manifold, a manually operable fuel control device for regulating flow of fuel through said main fuel conduit, a by-pass conduit for supplying fuel to said starting nozzle only and arranged to by-pass said manifold, valve means controlling flow of fuel through said by-pass'conduit, and fuel pressure responsive means controlling said valve means whereby fuel flow through said by-pass conduit is stopped when the fuel presure in said main fuel conduit attains a predetermined value.

2. In a fuel supply and starting system for a gas turbine engine having a combustion chamber, a plurality of fuel nozzles arranged to discharge fuel under pressure for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, an ignition circuit including a sparking device for igniting the fuel discharged from said starting nozzle, a fuel manifold common to all of said nozzles including the starting nozzle, a fuel con-" 18 fuse valve in said by-pass conduit functioning to admit a predetermined quantity of starting fuel to said starting nozzle and thereafter close off the flow of starting fuel to said latter nozzle, and means for metering fuel to the manifold during the starting period.

14. A fuel supply and starting system as claimed in claim 13 wherein said metering means includes a dashpot type metering valve and means responsive to changes in the density of the air flowin to the engine is provided for adjusting the rate of movement of said valve.

15. In a fuel supply and starting system for a gas turbine engine having a combustion zone into which air is pressured by a compressor, a plurality of fuel nozzles arranged to discharge fuel under pressure into said zone for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, ignition means for igniting the fuel discharged from said starting nozzle, 3. fuel manifold common to all of said nozzles including the starting nozzle, a main fuel control device for-regulating flow of fuel to said manifold during normal engine speeds, a starting fuel conduit lay-passing said device and manifold for conducting fuel to said starting nozzle, a device such as a hydraulic fuse valve interposed in said by-pass conduit functioning to measure the quantity of fuel fed to said starting nozzle and thereafter shut off flow 1 of fuel to said nozzle, a metering valv arranged to meter, at any given'engine operating condition, a predetermined quantity of the fuel flowing through said starting fuel conduit to the znanifold during the starting period, a piston connected to said metering valve, means for communicating fuel under pressure to said piston to actuate the latter, and means responsive to changes in a parameter affecting engine operation for adjusting the rate of travel of said piston.

16. In a fuel supply and starting system for a gas turbine engine having a combustion zone, a plurality of fuel nozzles arranged to discharge fuel under pressure into said zone for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, an electrical ignition circuit including an ignition device for igniting the fuel discharged from said starting nozzle, a fuel manifold common to all of said nozzles including the starting nozzle, a main fuel control device for regulating flow of fuel to said manifold during normal engine operation, starting fuel conduit means which by-passes said manifold for conducting fuel to said starting nozzle independently of the said manifold and which by-passes said device for conducting fuel to said manifold, a device interposed in said bypass conduit functioning to regulate the quantity of fuel passed to said starting nozzle, and a metering valve arranged to meter the fuel flowing through said starting fuel conduit to the manifold during the starting period.

17. In a fuel supply and starting system for a gas turbine engine having a combustion zone, a plurality of fuel nozzles arranged to discharge fuel under pressure into said zone for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, means for igniting the fuel discharged from said starting nozzle, a fuel manifold common to all of said nozzles including the startingnozzle, a fuel control device for regulating the flow of fuel to said manifold, means for pressurizing fuel to and through said device and manifold, a starting fuel conduit by-passing said device and manifold for conducting fuel under pressure to said startin nozzle, and means operable as a function of manifold pressure for admitting starting fuel to said starting nozzle when the pressure in the manifold is at a predetermined low value and for closing off starting fuel to the starting nozzle at a predetermined higher manifold pressure.

18. In a fuel supply and starting system for a gas turbine engine having a combustion chamber, a plurality of fuel nozzles arranged to discharge fuel under pressure for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, means for igniting the fuel discharged from said starting nozzle, a fuel manifold common to all of said nozzles including the starting nozzle, a fuel control device for regulating the flow of fuel to said manifold during normal engine operation, means for pressurizing fuel to and through said device and manifold, a starting fuel conduit by-passing said device and manifold for conducting fuel under pressure to said starting nozzles, a flow control device in said by-pass conduit upstream of said nozzles, and means responsive to manifold pressure for automatically admitting fuel to said starting nozzle by way of said starting fuel conduit and flow control device when the pressure in the manifold is at a predetermined low value and for closing off such fuel to the starting nozzle at a predetermined higher manifold pressure.

19. In a fuel supply and starting system for a gas turbine engine having a combustion zone, a plurality of fuel nozzles arranged to discharge fuel under pressure into said zone for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, ignition means for igniting the fuel discharged from said starting nozzle, a fuel manifold common to all nozzles including the starting nozzle, a fuel control device for regulating flow of fuel under pressure to said manifold, a conduit for starting fuel by-passing said device and manifold and terminating at the starting nozzle, a fuel inlet valve for admitting fuel to said starting fuel conduit, a metering valve of the dashpot type arranged to pass a certain quantity of fuel to the manifold when starting fuel is first admitted to said starting fuel conduit, said metering valve being responsive to starting fuel pressure and being spring-urged to return position against such pressure and during such return movement functioning to meter fuel to the manifold to gradually increase the pressure therein so that the engine will gradually accelerate to a selfsustaining speed without overtemperature, and another valve responsive to fuel pressure for automatically cutting off flow of starting fuel to the starting nozzles subsequent to ignition of the starting fuel.

20. A fuel supply and starting system as claimed in claim 13 wherein said metering means includes a dashpot type metering valve and means operative as a function of engine speed is provided for adjusting the rate of movement of-said valve.

21. In a fuel supply and starting system for a gas turbine engine having a combustion zone, a plurality of fuel nozzles arranged to discharge fuel under pressure for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, ignition means for igniting the fuel discharged from the starting nozzle, a fuel manifold common to all of said nozzles including the starting nozzle, a main fuel control device for regulating flow of fuel to said manifold and nozzles when the engine attains a self-sustaining speed, a starting fuel conduit arranged to conduct starting fuel to said starting nozzle, said conduit by-passing said manifold, means for supplying a regulated quantity of starting fuel to the starting nozzle through said conduit, and means controlled as a function of starting fuel pressure for metering fuel to the fuel manifold during the starting period.

22. In a fuel supply and starting system for a gas turbine engine having a combustion zone, a plurality of fuel nozzles arranged to discharge fuel under pressure for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, ignition means for igniting the fuel discharged from the starting nozzle, a fuel manifold common to all of said nozzles including the starting nozzle, a main fuel control device for regulating flow of fuel to said manifold and nozzles when the engine attains a self-sustaining speed, a starting fuel conduit ar ranged to conduct starting fuel to said starting nozzle, said conduit by-passing said manifold, means defining a metering orifice through which fuel is metered to said manifold during the starting period, a movable valve for varying the area of said orifice as a function of starting fuel pressure, and means for automatically effecting a predetermined rate of travel of said valve.

23. A fuel supply and starting system for a gas turbine engine as claimed in claim 22, wherein said valve is connected to a dash-pot piston exposed to starting fuel and a calibrated spring is provided for moving said piston.

24. A fuel supply and starting system for a gas turbine engine as claimed in claim 22 wherein said valve is connected to a spring-pressed dashpot piston which is moved in a direction to ini- 18 tially restrict said orifice in response to the build up of pressure of fuel at the starting nozzle and in the opposite direction by spring force, and, a fuel pressure-responsive valve is provided for cutting off flow of starting fuel to the starting nozzle.

25. In a fuel supply and starting system for a gas turbine engine having a combustion chamber, a plurality of fuel nozzles arranged to discharge fuel under pressure for admixture with air for effecting combustion, at least one of said nozzles functioning as a starting nozzle, an ignition circuit including a sparking device for igniting the fuel discharged from said starting nozzle, a fuel manifold common to all of said nozzles including the starting nozzle, a fuel control device for regulating flow of fuel to said manifold, a starting fuel conduit for conducting fuel to said starting nozzle and arranged to by-pass said manifold, valve means controlling flow of fuel through said starting fuel conduit, means for effective closure of said valve means and breaking of the ignition circuit, and means adapted to respond to a predetermined combustion chamber temperature for effecting operation of said, valve closing and circuit breaking means.

ANDREW A. KUZMITZ.

References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 980,801 Kraus Jan. 3, 1911 1,820,612 Good et al. Aug. 25, 1931 2,056,198 Lasley Oct. 6, 1936 2,096,184 Lasley Oct. 19, 1937 2,112,672 Lasley Mar. 29, 1938 2,199,454 Andler et a1. May 7, 1940 

